Flutter-resistant transonic turbomachinery blades and methods for reducing transonic turbomachinery blade flutter are provided. The flutter-resistant transonic turbomachinery blade comprises a transonic turbomachinery blade (14) that includes opposite pressure (20) and suction (18) surfaces extending longitudinally in span from a root (13) to an opposite tip (17), and extending axially in chord between opposite leading (22) and trailing (24) edges. The flutter-resistant transonic turbomachinery blade includes a local positive camber (32) in or proximate a predicted local region of supersonic flow (30) over the transonic turbomachinery blade. The method comprises predicting a local region of supersonic flow over the transonic turbomachinery blade and inducing the local positive camber to the transonic turbomachinery blade in or proximate the predicted region of supersonic flow.
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